XFOIL Version 6.96 Calculated polar for: FX 76-MP-120 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 0.2056 0.08761 0.08410 -0.1620 0.8340 0.0225 -9.750 0.2053 0.08470 0.08119 -0.1660 0.8309 0.0235 -9.500 0.2119 0.08212 0.07863 -0.1671 0.8283 0.0236 -9.250 0.2170 0.07870 0.07524 -0.1681 0.8258 0.0238 -9.000 0.2307 0.07646 0.07299 -0.1679 0.8235 0.0242 -8.750 0.2443 0.07472 0.07123 -0.1683 0.8212 0.0248 -8.500 0.2545 0.07259 0.06909 -0.1694 0.8189 0.0252 -8.250 0.2661 0.07062 0.06710 -0.1707 0.8163 0.0269 -8.000 0.2658 0.06811 0.06465 -0.1720 0.8135 0.0286 -7.750 0.2625 0.06521 0.06180 -0.1738 0.8099 0.0291 -7.500 0.2655 0.06273 0.05934 -0.1743 0.8069 0.0292 -7.250 0.2609 0.05930 0.05593 -0.1742 0.8041 0.0296 -7.000 0.2695 0.05725 0.05386 -0.1746 0.8018 0.0299 -6.750 0.2786 0.05558 0.05222 -0.1748 0.7993 0.0303 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0.03491 -0.1304 0.1952 1.0000 13.000 1.7213 0.04282 0.03698 -0.1286 0.1803 1.0000 13.250 1.7208 0.04520 0.03929 -0.1266 0.1643 1.0000 13.500 1.7195 0.04771 0.04174 -0.1248 0.1481 1.0000 13.750 1.7184 0.05024 0.04421 -0.1230 0.1320 1.0000 14.000 1.7157 0.05301 0.04692 -0.1213 0.1152 1.0000 14.250 1.7083 0.05634 0.05014 -0.1194 0.0955 1.0000 14.500 1.7022 0.05962 0.05334 -0.1178 0.0775 1.0000 14.750 1.6928 0.06337 0.05700 -0.1162 0.0603 1.0000 15.000 1.6843 0.06715 0.06072 -0.1149 0.0455 1.0000 15.250 1.6745 0.07124 0.06476 -0.1137 0.0336 1.0000 15.500 1.6661 0.07527 0.06878 -0.1128 0.0250 1.0000 15.750 1.6588 0.07929 0.07282 -0.1121 0.0199 1.0000 16.000 1.6529 0.08325 0.07684 -0.1116 0.0168 1.0000 16.250 1.6477 0.08723 0.08092 -0.1113 0.0148 1.0000 16.500 1.6433 0.09115 0.08493 -0.1111 0.0133 1.0000